JP2016516976A - Removable swirler assembly for combustion liner - Google Patents

Abstract

A new and improved swirler assembly for use in a combustion liner of a gas turbine engine is disclosed. The swirler assembly is removable and sized to provide improved assembly, repairability and attachment in the combustion liner. The swirler assembly includes a premixing tube, a premixing swirler, and a plurality of axially spaced mounting blocks for receiving removable fixtures for securing the swirler assembly to the combustor. .

Description

This application claims priority from US Provisional Patent Application No. 61 / 815,835, filed Apr. 25, 2013. Depending on the subject, the name of the invention is “PREMIXER ASSEMBLY FOR GAS TURBINE COMBUSTOR” (agent number PSM-317 / PSSF.199281) and “SWIRLER ASSEMBLY AND STIFFENING MECHANISM FOR PREMIXER ASSEMBLY OF A GAS TURBINE COMBUSTOR” No. PSM-318 / PSSF.199282), which is assigned to the same assignee as the present application regarding a US non-provisional patent application by a joint applicant.

TECHNICAL FIELD The present invention relates generally to gas turbine combustors. In particular, the present invention provides a removable swirler portion of a combustion liner having features designed to enhance combustor performance and increase component life through improved assembly and disassembly techniques and improved cooling structures. Is directed.

Background of the Invention In a typical gas turbine engine, a compressor having alternating stages of rotor and fixed blades is connected to the turbine via an axial shaft, which is also an alternating rotor and fixed blade. Has a stage. The compressor stage is reduced in size to compress the air passing through the compressor stage. The compressed air is then supplied to one or more combustors, which mix the air with the fuel. An ignition source in the vicinity of the one or more combustors ignites the mixture and forms hot combustion gases. The expansion of the hot combustion gases drives a turbine stage connected to the compressor via an axial shaft. The exhaust gas can then be utilized as a propulsion source or to generate steam by an exhaust heat recovery boiler, or in a power plant to rotate a shaft connected to a generator for producing electricity. it can.

  Gas turbine engine combustion systems can have a variety of configurations. Combustion system for a gas turbine engine includes a single combustion chamber, a plurality of individual combustion chambers spaced about the engine axis, a plenum combustion system, or various other combustion systems Can do. Depending on the engine geometry, performance requirements and physical operating position, the exact combustor arrangement will vary.

  One such combustion system includes a casing secured to an engine frame, a combustion liner secured within at least a portion of the casing, and fuel (gas, liquid, or both) for injection into a combustion chamber. One or more fuel nozzles positioned within or adjacent to the combustion liner. The combustion system is fluidly connected to the engine. In particular, the casing and liner arrangement provides a path for air from the compressor to enter the combustion system. In the combustion system, air is mixed with fuel from one or more fuel nozzles. The fuel air mixture is ignited by an ignition source such as a spark igniter. Hot combustion gases travel through the combustion liner and usually one or more transition pieces into the turbine. A transition piece is basically a duct having a geometry that changes from the shape of the combustor to the inlet of the turbine.

  The combustion liner is at the center of combustor operation. Combustion liner geometry is determined by various factors including engine operating parameters, performance requirements and available geometry. While the combustion liner geometry can vary, the combustion liner typically contains a fuel nozzle, mixes fuel and air, and has at least a portion for confining the reaction when the fuel air mixture is ignited.

  Prior art combustion liners meet certain performance requirements, but also exhibit various drawbacks. For example, conventional combustion liners are primarily or exclusively welded assemblies that make it difficult for an operator or repair facility to access all components of the combustion liner to be repaired. In addition, a conventional combustor design of similar construction was able to operate for about 8000 hours prior to refurbishment or replacement. In an attempt to improve gas turbine engine efficiency, there is a strong demand among operators to be able to extend the time frame between repairs to reduce engine downtime and repair / overhaul costs.

SUMMARY In accordance with the present invention, a new and improved swirler assembly for use in a gas turbine engine combustion liner is provided. The swirler assembly is removable and sized to provide improved assembly, repairability and attachment in the combustion liner. The plurality of main swirler assemblies are disposed about the central axis within the combustion liner and are sized to accommodate a plurality of fuel nozzles.

  According to one embodiment of the present invention, a plurality of first mixing tubes, a premixing swirler disposed in the premixing tube, and a plurality of first mixing tubes disposed along the outer wall of the premixing tube near the inlet end. A first mounting block having one hole and a second mounting block also disposed along the outer wall of the premixing tube, wherein the plurality of second mounting blocks are spaced from the first mounting block. There is provided a swirler assembly for a gas turbine combustor comprising a second block having one or more second holes in a direction perpendicular to the one hole.

  According to another embodiment of the present invention, a first fixed block fixed to a body, comprising a front surface, an opposite rear surface, a substantially parallel side surface, an arched outer surface, and an arched shape A multi-point, multi-directional securing assembly is provided for use in a gas turbine combustor comprising a first mounting block having a plurality of holes disposed on an outer surface. The securing assembly also includes a second mounting block having one or more holes secured to the body, the plurality of holes in the first mounting block being one or more holes in the second mounting block. Is oriented substantially perpendicular to the.

  In accordance with yet another embodiment of the present invention, a removable swirler in a combustor comprising a generally cylindrical body, a center core, and a plurality of vanes extending between the center core and the generally cylindrical body. An assembly is provided. The removable swirler assembly also includes a first mounting block secured to the generally cylindrical body, the first mounting block having a front surface, an opposite rear surface, a generally parallel side surface, and an arcuate shape. An outer surface and a plurality of holes disposed in the arched outer surface. The removable swirler assembly also includes a second mounting block having one or more holes secured to the body, wherein the removable swirler includes first and second through a plurality of removable fasteners. Both mounting blocks are secured to the combustor.

  Additional advantages and features of the present invention will be set forth in part in the description which follows, and in part will be apparent to those of ordinary skill in the art upon review of the following description or may be learned from practice of the invention. The present invention will now be described with particular reference to the accompanying drawings.

BRIEF DESCRIPTION OF THE DRAWINGS The present invention will be described in detail below with reference to the accompanying drawings.

1 is a partial cross-sectional view of a prior art gas turbine engine in which a combustion system according to one embodiment of the present invention is available. 2 is a cross-sectional view of a prior art gas turbine combustor operable within the gas turbine engine of FIG. 1 is a perspective view of a combustion liner that includes one embodiment of the present invention. FIG. 1 is a cross-sectional view of a combustion liner including one aspect according to one embodiment of the present invention. FIG. 5 is an alternative view of the cross-sectional view of FIG. 4 including one embodiment of the present invention. 1 is a cross-sectional view of a combustion liner as viewed along a swirler assembly, according to one embodiment of the present invention. FIG. FIG. 7 is an alternative view of the cross-sectional view of FIG. 6 according to one embodiment of the present invention. FIG. 4 is a perspective view of a swirler assembly portion of the combustion liner of FIG. 3 according to one embodiment of the present invention. FIG. 4 is a detailed cross-sectional view taken along the inlet portion of the combustion liner of FIG. 3 including a cross-sectional view of a swirler assembly according to one embodiment of the present invention. 1 is a partial cross-sectional view of a fuel liner swirler assembly, according to one embodiment of the present invention. FIG.

DETAILED DESCRIPTION The subject matter of the present invention is described herein with clarity so as to meet statutory requirements. However, the description itself is not intended to limit the scope of this patent. Rather, the inventors include various different components, component combinations, steps or combinations of steps similar to those described in this document in connection with other current or future technologies, It is envisioned that the subject matter recited in the claims may be embodied in other forms.

  Referring first to FIG. 1, a prior art gas turbine engine 100 is shown in partial cross-sectional view. The gas turbine engine 100 generally has an outer casing 102 that surrounds a major portion of the engine. A shaft 104 extends axially along the engine axis AA and is connected to the compressor 106 and the turbine 108. The compressor 106 receives air through the inlet region 110 and directs the air through alternating rows of decreasing sized rotor blades and stationary blades, thereby directing the air as it passes. Compress, thereby increasing the temperature and pressure of the air. The compressed air is then directed through one or more combustion systems 112 where the fuel and air are mixed and ignited to form hot combustion gases. The hot combustion gases are then directed into the gas turbine 108 and pass through alternating rows of increasing size rotor blades and stationary blades, causing the fluid to expand and the energy of the combustion gases to be transferred to the machine. Converted to work, the shaft 104 is driven. The shaft 104 may be connected to a generator shaft for power generation (not shown).

  FIG. 2 shows a cross-sectional view of a prior art gas turbine engine combustor 200. As such, the exemplary gas turbine combustor 200 includes a casing 202, a cover 204, one or more injectors 206, and a combustion liner 208. Transition piece 210 connects combustion liner 208 to the inlet of turbine 212.

  The present invention is shown in detail in FIGS. 3-10 and discloses a new and improved removable swirler assembly for use in a combustor of a gas turbine engine. Referring first to FIGS. 3-7, a combustion liner 300 having a removable swirler assembly 332 is shown. Combustion liner 300 includes a generally cylindrical liner body 302 having an inlet end 304, an outlet end 306 or discharge end, and an axis BB extending through the combustor. Although the combustion liner 300 is generally cylindrical in cross section, it is understood that the combustion liner 300 may vary in shape and may have a tapered section or a section of varying diameter. The combustion liner 300 is generally manufactured from a rolled metal sheet. The rolled metal sheet is welded along an axial seam and can be shaped or expanded into a cylindrical structure that varies depending on the specific combustion geometry. The combustion liner 300 is preferably made from a heat resistant alloy, such as Haynes 230, that can withstand increased combustor conditions above about 1500 degrees Fahrenheit. Alternative materials such as Hastelloy X or Inconel may be used.

  The combustion liner 300 further includes an inlet ring basket 308 secured to the generally cylindrical body 302. The inlet ring basket 308 consists of a number of generally axially oriented spindles 310 connected to the forward ring 312 and forwardly from the inlet end 304 of the combustion liner 300 as shown in FIGS. It is extended. The forward ring 312 is spaced from the combustion liner 300, thereby allowing a group of fuel nozzles (not shown) to position the fuel nozzle at an appropriate axial position within the combustor. A combined arrangement can be established. The inlet ring basket 308 may be a manufactured component or casting and is preferably manufactured from a stainless steel material. Referring now to FIG. 10, as described in more detail below, the inlet ring basket 308 includes a plurality of radially inward extending from the inlet ring basket 308 that is used to secure the premix assembly 330. A protrusion 309 is also included. The protrusion 309 may be manufactured separately and welded to the inner ring basket 308 or cast as part of the inner ring basket 308.

  With reference to FIGS. 4-7, the combustion liner 300 also includes a premix assembly 330. One component of the premixer 330 is one or more removable swirlers 332. With reference now to FIGS. 8-10, a swirler assembly 332 is shown in the premix assembly 330. The swirler assembly 332 includes a premix tube 342 having an outlet end 342B opposite the inlet end 342A and a longitudinal axis C-C extending therethrough. The swirler assembly 332 also has a premixing swirler 336 disposed within the premixing tube 342 within which the premixing swirler 336 provides swirl for the flow through the premixing tube 342. A plurality of turning vanes 338 are provided. In the embodiment shown in FIGS. 8-10, the premixing tube 342 is substantially cylindrical. However, alternative shapes for the premix tube 342 are possible.

  The swirler assembly 332 also has two mounting blocks for securing the swirler assembly to the gas turbine combustor. The first mounting block 344 is disposed in the vicinity of the inlet end portion 342 </ b> A of the premixing tube 342 along the outer wall of the premixing tube 342. The first mounting block 344 has a first front surface 344A, an opposite first rear surface 344B, a pair of substantially parallel side surfaces 345, and an outer surface 347. The outer surface 347 may have an arcuate shape along at least a portion of the outer surface, which allows the mounting block 344 to conform to the shape of the inner ring basket 308. The outer surface 347 is utilized to set the radial position of the swirler assembly 332 and the swirler assembly contact with the inner ring basket 308, which allows for narrower dimensional control of the swirler assembly 332 relative to the fuel nozzle. The first mounting block 344 includes a plurality of orientated substantially perpendicular to the longitudinal axis CC of the premix tube 342 disposed on the arcuate outer surface 347, as shown in FIG. It also has a first hole 348.

  The swirler assembly 332 also has a second mounting block 346 disposed along the outer wall of the premixing tube 342 and spaced axially from the first mounting block 344. The second mounting block 346 has a second front surface 346A and an opposite second rear surface 346B that attaches the swirler assembly 332 to an appropriate axial position in the combustor. Are machined to a predetermined size to form a specific axial dimension. To position swirler assembly 332 in the proper axial position, second mounting block 346 has a relief 360 machined into second rear surface 346B. The second mounting block 346 also has one or more second holes 356 that extend through the second mounting block 346 in a direction substantially perpendicular to the plurality of first holes 348.

  In the embodiment of the invention shown in FIGS. 8-10, the second mounting block 346 is directly axially aligned with the first mounting block 344. However, depending on the combustor geometry, the first and second mounting blocks 344, 346 may be circumferentially offset relative to each other without being axially aligned.

  Each of the first mounting block 344 and the second mounting block 346 is fixed to the premixing tube 342. Different mounting methods for the mounting blocks can be implemented. In one embodiment, the first mounting block 344 and the second mounting block 346 are welded to the premix tube 342. A bead of matching weld material (compatible between the material of the premix tube 342 and the mounting blocks 344, 346) is formed at the intersection of the mounting block and the premix tube 342.

  An alternative method of securing the first and second mounting blocks 344, 346 to the premix tube 342 is by brazing. Brazing joints help to form a more complete joint when all surfaces of the mounting block that are in contact with the premix tube 342 are joined to the premix tube 342. Conversely, melt bonding exclusively secures the mounting block to the premixing tube 342 at the edge where the mounting block contacts the premixing tube.

  In yet another embodiment, the mounting blocks 344, 346 may be integrated with the premixing tube 342. The mounting blocks 344 and 346 can be incorporated into the premixing tube 342 by casting or forging.

  The exact size, spacing and number of holes in the first mounting block 344 and the second mounting block 346 may vary, combustor geometry, swirler assembly 332 size, mechanical and thermal effects occurring in the swirler assembly 332. Depends on various factors such as heavy load. In one embodiment of the present invention shown in FIGS. 8-10, the first mounting block 344 has two first holes 348, which are longitudinal axes C. Oriented approximately perpendicular to -C. The second mounting block 346 has one or more second holes 356, and the embodiments shown in FIGS. 8-10 use a single second hole 356. However, more than one second hole 356 may be required to secure the swirler assembly 332 to the combustor. In the embodiment shown in FIGS. 8 to 10, the second hole 356 is substantially parallel to the axis CC.

  As mentioned above, the swirler assembly 332 is designed to be easily removed from the combustor for easier maintenance and repair. Accordingly, a plurality of removable fasteners 350, 358 are utilized to secure swirler assembly 332 to the combustor. In one embodiment, a removable fixture, such as a bolt, engages a corresponding thread pattern in the plurality of first holes 348 and the one or more second holes 356. However, a thread pattern is one way to secure a removable fixture. Alternatively, one or more holes 356 may be through holes (i.e., not threaded) and a nut that abuts surface 346A may be used. Further, bolts / studs may be welded / assembled instead of holes 356 and then nuts may be placed on the surface of the dome plate 334.

  The swirler assembly 332 is arranged to be in fluid connection with an adjacent tube 352, also referred to as a hoover, so that fluid and air flows through the hoover from the swirler assembly 332 to the mixing zone of the combustion liner 300. That is, swirler assembly 332 is positioned adjacent to or slightly engaging tube 352. To ensure that the swirler assembly 332 is in the proper radial position in the combustion liner and forms a radial clearance with the tube 352, a plurality of standoffs 354 are adjacent to the outer end 342B, respectively. The premixing tube 342 is disposed around the outer surface.

  As described above, the swirler assembly 332 is removably secured to the combustor via a plurality of fasteners 350, 358, such as bolts or other means. For example, as shown in FIGS. 6-10, the main swirler assembly 332 is secured to the dome plate 334 by fasteners 350, 358 that pass through the first hole 348 and the second hole 356. . Better positioning and tolerance adjustment of the swirler assembly 332 relative to the premixing assembly 330 and the combustion liner 300 is achieved through the use of fixtures 350, 358 oriented both radially and axially. Further, the removable fixation of swirler assembly 332 to premix assembly 330 allows overhaul and repair accessibility to premix assembly 330 to be achieved with a prior art combustor having a swirler assembly welded to the premix assembly. Compared to significantly increased. As those skilled in the art will appreciate, in addition to accessibility issues, welding of the swirler assembly also causes deformation of the swirler assembly. Therefore, deformation can affect flow control.

  The swirler assembly 332 is preferably made from a material similar to the premix assembly 330, such as a type of stainless steel. The swirler assembly 332 may be a manufactured assembly of various machined parts or castings.

  Referring now to FIGS. 9 and 10, a swirler assembly 332 is shown mounted within the premix assembly 330. As described above, the swirler assembly 332 is secured by fixtures 350, 358 that are oriented both radially and axially. The swirler assembly 332 is such that the standoff 354 provides radial clearance with respect to the tube 352 so that the second mounting block 346 contacts the protrusion 309 of the inlet ring basket 308 at the appropriate axial position by the relief 360. Then, it is slid to a predetermined position.

  The invention has been described with reference to particular embodiments that are illustrative rather than restrictive in all respects. Alternative embodiments and the required operation will be apparent to those skilled in the art to which the present invention belongs without departing from the scope of the invention.

  From the foregoing description, it can be seen that the present invention is well adapted to accomplish all its objectives and challenges, with other advantages that are apparent and inherent to the system and method. It will be understood that certain features and combinations may be utilized and used without reference to other features and combinations. This is considered by the claims and in the claims.

Claims (19)

A swirler assembly for a gas turbine combustor comprising:
A premixing tube having an inlet end, an opposite outlet end, and a longitudinal axis extending through the inlet end and the outlet end;
A premixing swirler having a plurality of turning vanes disposed in the premixing tube for swirling the passing flow;
A first mounting block having a plurality of first holes disposed along the outer wall of the premixing tube in the vicinity of the inlet end and oriented substantially perpendicular to the longitudinal axis;
A second mounting block spaced from the first mounting block along an outer wall of the premixing tube, wherein the second mounting block is perpendicular to a plurality of the first holes; A second mounting block having one or more second holes extending through the mounting block;
A swirler assembly comprising:   The swirler assembly of claim 1, wherein the premixing tube is substantially conical.   The swirler assembly of claim 1, wherein each of the first mounting block and the second mounting block is secured to the premixing tube.   4. A swirler assembly according to claim 3, wherein the first and second mounting blocks are secured to the premix tube by welding or brazing.   The swirler assembly of claim 1, wherein the plurality of holes in the first mounting block includes at least two holes.   The swirler assembly of claim 1, wherein the one or more second holes are threaded.   The second mounting block has a second rear surface opposite to the second front surface, the second rear surface being finish machined to a predetermined axial dimension. Swirler assembly. A multi-point multi-directional stationary assembly for use in a gas turbine combustor,
A first mounting block fixed to the body, having a first front surface, an opposite first rear surface, a pair of side surfaces, an outer surface, and a plurality of holes disposed on the outer surface; A first mounting block;
A second mounting block secured to the body, the second mounting block having one or more holes disposed in the second mounting block;
And wherein the second mounting block is spaced axially from the first mounting block.   The fixation assembly of claim 8, wherein the outer surface is arcuate in a region surrounding at least the plurality of holes.   The fixation assembly of claim 8, wherein the first mounting block is fixed to the body by welding or brazing.   The fixation assembly of claim 8, wherein the second mounting block is fixed to the body by welding or brazing.   The fixation assembly of claim 8, wherein the first and second mounting blocks are incorporated into the body.   The fixation assembly of claim 8, wherein the plurality of holes in the first mounting block are substantially perpendicular to the one or more holes in the second mounting block. A removable swirler assembly in a combustor, comprising:
An almost cylindrical body,
A center core disposed in the cylindrical body near the entrance of the substantially cylindrical body;
A plurality of vanes extending between the center core and the generally cylindrical body;
A first mounting block fixed to the substantially cylindrical body, the first mounting block having a first front surface, an opposite rear surface, a pair of side surfaces, and an outer surface on which a plurality of holes are disposed. A mounting block of
A second mounting block secured to the generally cylindrical body, the second mounting block having one or more holes disposed therein;
The removable swirler is fixed to the combustor in both the first mounting block and the second mounting block by a plurality of removable fasteners. Swirler assembly.   The removable swirler of claim 14, wherein the plurality of vanes are oriented to impart a swirl to the passing air and fuel flow.   The removable swirler of claim 14, wherein the first mounting block extends a greater circumferential distance than the second mounting block.   The removable swirler of claim 14, wherein the plurality of holes in the first mounting block are substantially perpendicular to a single hole in the second mounting block.   The removable swirler of claim 14, further comprising a plurality of fasteners disposed within a plurality of openings in the first mounting block for securing the swirler to the combustor.   The removable swirler of claim 14, wherein an outer surface of the first mounting block is arched in a region near at least a plurality of the holes.

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